JPH0751888B2 - Cooling shroud support - Google Patents
Cooling shroud supportInfo
- Publication number
- JPH0751888B2 JPH0751888B2 JP4019345A JP1934592A JPH0751888B2 JP H0751888 B2 JPH0751888 B2 JP H0751888B2 JP 4019345 A JP4019345 A JP 4019345A JP 1934592 A JP1934592 A JP 1934592A JP H0751888 B2 JPH0751888 B2 JP H0751888B2
- Authority
- JP
- Japan
- Prior art keywords
- hanger
- outlet
- shroud support
- shroud
- fluid
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
- F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
【０００１】[0001]
【産業上の利用分野】本発明はガスタービンエンジンの
翼端とシュラウドとの間隙の制御に関し、特に、間隙制
御を改善するように冷却されるシュラウド支持体に関す
る。FIELD OF THE INVENTION The present invention relates to gas turbine engine tip to shroud clearance control, and more particularly to a shroud support which is cooled to improve clearance control.
【０００２】[0002]
【従来の技術】従来のガスタービンエンジンは周方向に
相隔たる多数の動翼を備えたタービンを含み、動翼の先
端は環状の静止シュラウドから半径方向内方に離隔して
それとの間に間隙を画成する。翼端間隙をなるべく小さ
くすることにより動翼周囲の燃焼ガスの漏れを最少にし
てタービンの効率を高める必要がある。しかし、運転中
の翼端間隙は、動翼とシュラウドとの熱膨縮差に適応し
て両者間の望ましくない摩擦を防ぐのに充分な程大きく
なければならない。BACKGROUND OF THE INVENTION A conventional gas turbine engine includes a turbine having a number of circumferentially spaced blades, the tips of the blades being spaced radially inward from a stationary annular shroud and having a gap therebetween. Define. It is necessary to minimize the leakage of combustion gas around the moving blades and improve the efficiency of the turbine by making the tip clearances as small as possible. However, the tip clearance during operation must be large enough to accommodate the differential thermal expansion and contraction of the blade and shroud to prevent unwanted friction between them.
【０００３】翼端間隙は、従来、エンジンの様々な定常
運転状態において様々な値をもち、また、エンジン出力
値を変えるにつれて発生するエンジンの様々な過渡運転
状態中も様々な値を取る。過渡翼端間隙制御は重要な問
題である。なぜなら、翼端とシュラウドとの熱差動は、
翼端摩擦のおそれを減らすために適度に大きくすべき最
小値をもつからで、この最小値は狭点（pinch point)の
値とも呼ばれる。しかし、狭点の値を適度に大きくして
も、過渡応答における他の時点と、定常状態の運転中と
に発生する翼端間隙は狭点より必ず大きいので、翼端を
通り越す燃焼ガスの漏れを増加させてタービン性能を減
らす。Tip clearances conventionally have different values under different steady-state operating conditions of the engine, and also during different transient operating conditions of the engine which occur as the engine power value is varied. Transient tip clearance control is an important issue. Because the thermal differential between the blade tip and the shroud is
This minimum value is also called the pinch point value because it has a minimum value that should be reasonably large to reduce the risk of tip friction. However, even if the value of the narrow point is moderately increased, the blade tip clearance that occurs at other points in the transient response and during steady-state operation is always larger than the narrow point, so the leakage of combustion gas past the blade tip To reduce turbine performance.
【０００４】さらに、ガスタービンエンジンは通例軸対
称であるが、タービンシュラウドの環境における温度は
エンジン中心線について周方向に必ずしも均等ではな
い。例えば、回収熱交換器を含むガスタービンエンジン
の一例では、圧縮機吐出し空気が回収熱交換器により加
熱され、そして高圧タービン（ＨＰＴ）のシュラウド近
辺でエンジンケーシングの頂部と底部近くに配置した２
つの周方向に相隔たる回収熱交換器導管を経て燃焼器に
導かれる。従って、ＨＰＴシュラウドは、温度がほぼ周
方向で変わる環境に配置され、比較的高い温度が回収熱
交換器導管の近くで発生しそして比較的低い温度が両導
管の間で発生する。従って、ＨＰＴの翼端間隙は、周方
向に均等な冷却空気をシュラウドに供給する従来のよう
に冷却されるシュラウド支持体の場合、エンジン中心線
について周方向に一様でない。Moreover, although gas turbine engines are typically axisymmetric, the temperature in the turbine shroud environment is not necessarily uniform circumferentially about the engine centerline. For example, in one example of a gas turbine engine that includes a recovery heat exchanger, the compressor discharge air is heated by the recovery heat exchanger and is located near the top and bottom of the engine casing near the high pressure turbine (HPT) shroud.
It is led to the combustor via two circumferentially separated recovery heat exchanger conduits. Therefore, the HPT shroud is placed in an environment where the temperature varies substantially circumferentially, with relatively high temperatures occurring near the recovery heat exchanger conduit and relatively low temperatures occurring between both conduits. Thus, the HPT tip clearance is not circumferentially uniform about the engine centerline for conventionally cooled shroud supports that provide circumferentially uniform cooling air to the shroud.
【０００５】[0005]
【発明の目的】従って、本発明の目的は、翼端間隙の周
方向変動を減らすために周方向において比較的均等に冷
却されるシュラウド支持体を提供することである。OBJECTS OF THE INVENTION Accordingly, it is an object of the present invention to provide a shroud support that is relatively evenly cooled in the circumferential direction to reduce circumferential variations in tip clearance.
【０００６】[0006]
【発明の概要】シュラウド支持体が、環状ケーシング
と、このケーシングから半径方向内方に離隔した環状ハ
ンガとを含む。ハンガは、その内部に周方向に延在する
流れダクトを有し、また複数の周方向に相隔たるタービ
ン動翼の半径方向外側に配置し得るシュラウドを半径方
向に支持するベースを有する。冷却流体をハンガの流れ
ダクト内で周方向に導くことによりハンガを冷却し、こ
うして、周方向翼端間隙の均等度を高めるとともに、シ
ュラウドと翼端との熱変位をより良く整合する。SUMMARY OF THE INVENTION A shroud support includes an annular casing and an annular hanger radially inwardly spaced from the casing. The hanger has a circumferentially extending flow duct therein and also has a base radially supporting a plurality of circumferentially spaced shrouds that may be disposed radially outward of the turbine blades. Cooling the hanger by guiding cooling fluid circumferentially within the hanger's flow duct thus increasing the uniformity of the circumferential tip clearance and better matching the thermal displacement between the shroud and the tip.
【０００７】本発明は、他の目的と利点とともに、添付
図面と関連する以下の詳述からさらに明らかとなろう。The invention, together with other objects and advantages, will be more apparent from the following detailed description in conjunction with the accompanying drawings.
【０００８】[0008]
【実施例の記載】図１はガスタービンエンジンの一例１
０の概略図である。エンジン１０には従来の圧縮機１４
と環状燃焼器１６と高圧タービンノズル１８と高圧ター
ビン（ＨＰＴ）２０と低圧タービン（ＬＰＴ）２２が含
まれ、直流連通をなしかつエンジンの軸方向中心線１２
の周りに同軸的に配置されている。従来のＨＰＴ軸２４
が圧縮機１４をＨＰＴ２０に連接し、そして従来のＬＰ
Ｔ軸２６がＬＰＴ２２から突出して負荷（図示せず）に
動力を伝える。DESCRIPTION OF THE EMBODIMENTS FIG. 1 shows an example 1 of a gas turbine engine.
FIG. The engine 10 has a conventional compressor 14
And an annular combustor 16, a high pressure turbine nozzle 18, a high pressure turbine (HPT) 20 and a low pressure turbine (LPT) 22, which are in direct current communication and which have an axial centerline 12 of the engine.
Are arranged coaxially around. Conventional HPT shaft 24
Connects the compressor 14 to the HPT 20, and the conventional LP
The T shaft 26 projects from the LPT 22 and transmits power to a load (not shown).
【０００９】エンジン１０はさらに環状ケーシング２８
を含み、このケーシングは圧縮機１４を覆いそこから下
流に延びてＬＰＴ２２を覆っている。従来の回収熱交換
器３０がケーシング２８の外側に圧縮機１４とＬＰＴ２
２の間に配置されている。The engine 10 further includes an annular casing 28.
This casing covers the compressor 14 and extends downstream therefrom to cover the LPT 22. The conventional recovery heat exchanger 30 has the compressor 14 and the LPT 2 outside the casing 28.
It is located between two.
【００１０】エンジン１０の従来の運転中、周囲空気３
２が圧縮機１４に入って圧縮され圧縮空気流３４とな
る。圧縮空気流３４は従来のように適当な導管３０ａを
経て回収熱交換器３０を通り、そこでさらに加熱された
後、適当な導管３０ｂを経てケーシング２８を貫流し燃
焼器１６近辺に導かれる。加熱された圧縮空気流３４は
図２において回収熱交換器空気流３４ｂとして示されて
いるもので、その後燃焼器１６内で従来のように燃料と
混合して点火され、その結果燃焼ガス３６が発生しノズ
ル１８を経てＨＰＴ２０に入る。ＨＰＴ２０は燃焼ガス
３６からエネルギーを抽出しＨＰＴ軸２４を介して圧縮
機１４を駆動し、その後燃焼ガス３６はＬＰＴ２２に達
する。ＬＰＴ２２はさらに燃焼ガス３６からエネルギー
を抽出し、ＬＰＴ軸２６に連結した負荷（図示せず）を
駆動する。回収熱交換器３０は従来のように導管３０ｃ
によりＬＰＴ２２に接続され、燃焼ガス３６の一部分が
ＬＰＴ２２から回収熱交換器３０に導入され、同熱交換
器を通流する圧縮空気流３４を加熱する。During conventional operation of engine 10, ambient air 3
2 enters the compressor 14 and is compressed into a compressed air stream 34. Compressed air stream 34 passes through suitable conduit 30a through recovery heat exchanger 30 as is conventional, where it is further heated and then flows through casing 28 through suitable conduit 30b into the vicinity of combustor 16. The heated compressed air stream 34, shown in FIG. 2 as the recovered heat exchanger air stream 34b, is then conventionally mixed with fuel in the combustor 16 and ignited, resulting in combustion gas 36. It is generated and enters the HPT 20 through the nozzle 18. The HPT 20 extracts energy from the combustion gas 36 and drives the compressor 14 via the HPT shaft 24, after which the combustion gas 36 reaches the LPT 22. The LPT 22 further extracts energy from the combustion gas 36 and drives a load (not shown) connected to the LPT shaft 26. The recovery heat exchanger 30 has a conventional conduit 30c.
Is connected to the LPT 22, and a part of the combustion gas 36 is introduced from the LPT 22 to the recovery heat exchanger 30 to heat the compressed air flow 34 flowing through the heat exchanger 30.
【００１１】図１に示すように、２本の回収熱交換器導
管３０ｂが約１８０度離れた角位置でケーシング２８に
接続されている。エンジン１０の運転中、加熱された回
収熱交換器空気流３４ｂは両導管３０ｂを通ってケーシ
ング２８内に入り燃焼器１６と高圧ノズル１８とＨＰＴ
２０の上流端との近辺に達する。両導管３０ｂは１８０
度離れているので、ケーシング２８内の温度は周方向に
沿って変わり、最高温度が両導管３０ｂの近くで生じそ
して最低温度が両導管３０ｂ間のほぼ等角度または等距
離の位置で発生する。As shown in FIG. 1, two recovery heat exchanger conduits 30b are connected to the casing 28 at angular positions about 180 degrees apart. During operation of the engine 10, the heated recovery heat exchanger airflow 34b enters the casing 28 through both conduits 30b and the combustor 16, high pressure nozzle 18 and HPT.
Reach the vicinity of the upstream end of 20. Both conduits 30b are 180
Because of the degrees of separation, the temperature within casing 28 varies circumferentially, with the highest temperatures occurring near both conduits 30b and the lowest temperatures occurring at approximately equiangular or equidistant locations between both conduits 30b.
【００１２】従って、ケーシング２８内のＨＰＴ２０近
辺の環境温度のこの周方向変化は、動翼４４とシュラウ
ド４２との熱応答差と、翼端間隙の周方向変化とを減ら
す本発明によって提供されるような適当なシュラウド支
持体を必要とする。Thus, this circumferential change in ambient temperature near the HPT 20 within the casing 28 is provided by the present invention which reduces the thermal response difference between the blade 44 and the shroud 42 and the circumferential change in tip clearance. Such a suitable shroud support is required.
【００１３】さらに詳述すると、図２に示すように、エ
ンジン１０は本発明の一実施例によるタービンシュラウ
ド支持体３８をさらに含み、このシュラウド支持体は複
数の周方向に相隔たるボルト４０によりケーシング２８
に従来のように固定され支持されている。従来の環状タ
ービンシュラウド４２が、例えば複数の周方向に相隔た
るシュラウド部片の形態をなすものとして、従来のよう
にシュラウド支持体３８に結合されており、そしてＨＰ
Ｔ２０の第１段の複数の動翼４４から半径方向に所定の
ように隔たっている。各動翼４４は翼端４４ｂを有し、
この翼端はシュラウド４２から半径方向内方に離隔して
翼端間隙Ｃを画成する。More specifically, as shown in FIG. 2, engine 10 further includes a turbine shroud support 38 according to one embodiment of the present invention, the shroud support being casing by a plurality of circumferentially spaced bolts 40. 28
It is fixed and supported in the conventional manner. A conventional annular turbine shroud 42 is conventionally coupled to shroud support 38, for example in the form of a plurality of circumferentially spaced shroud pieces, and HP
It is separated from the plurality of blades 44 of the first stage of T20 in the radial direction by a predetermined distance. Each blade 44 has a tip 44b,
The tip is spaced radially inward from shroud 42 to define a tip clearance C.
【００１４】シュラウド支持体３８には環状ハンガ４６
が含まれ、中心線１２の周りに同軸的に配置されてお
り、この中心線はシュラウド支持体３８の中心線でもあ
る。ハンガ４６は、ほぼ円錐台形の一体の環状取付けフ
ランジ４８によりケーシング２８に固定されている。こ
のフランジは環状流路５０内でハンガ４６をケーシング
２８から半径方向内方に隔てており、環状流路５０はケ
ーシング２８とそれから半径方向内方に離隔した諸構成
部との間に画成されて回収熱交換器空気流３４ｂの一部
分を受入れる。図２に示した本発明の実施例では、ハン
ガ４６は横断面が概して長方形であり、そして軸方向に
相隔たる環状の前側レール５２と後ろ側レール５４を含
み、両レールは環状ベース５６から半径方向外方に突出
している。ベース５６は軸方向に相隔たる１対の従来の
外側フック５８を含み、両外側フックは周方向に延在
し、シュラウド４２の補完的な内側フック６０と従来の
ように結合してシュラウド４２をハンガ４６に半径方向
に保持する。The shroud support 38 includes an annular hanger 46.
Are located coaxially about the centerline 12, which is also the centerline of the shroud support 38. The hanger 46 is secured to the casing 28 by an integral annular mounting flange 48 that is generally frustoconical. The flange separates the hanger 46 radially inward from the casing 28 within the annular flow passage 50, the annular flow passage 50 being defined between the casing 28 and components radially inwardly spaced therefrom. And receives a portion of the recovered heat exchanger airflow 34b. In the embodiment of the invention shown in FIG. 2, the hanger 46 is generally rectangular in cross-section and includes axially spaced annular front and rear rails 52 and 54, both rails having a radius from an annular base 56. It projects outward in the direction. The base 56 includes a pair of axially spaced conventional outer hooks 58 that extend circumferentially and are conventionally coupled to the complementary inner hooks 60 of the shroud 42 to secure the shroud 42. The hanger 46 is held in the radial direction.
【００１５】ハンガ４６はまた軸方向に延在する環状頂
部６２を含み、この頂部はベース５６とほぼ平行に配置
されそれとの間に周方向に延在する流れダクト６４を画
成している。流れダクト６４は中心線１２の周りに同軸
的に配設されている。前側および後ろ側レール５２、５
４とベース５６は好ましくは互いに一体に形成され、こ
の一体物に頂部６２を例えばろう付けにより適当に接合
して密閉流れダクト６４を形成しうる。ベース５６は複
数の周方向に相隔たる放出孔６６を有し、これらの放出
孔は冷却流体６８を流れダクト６４からシュラウド４２
に衝突させるように導いてシュラウドの冷却に役立て
る。Hanger 46 also includes an axially extending annular top 62 which defines a circumferentially extending flow duct 64 disposed generally parallel to base 56. The flow duct 64 is coaxially arranged around the center line 12. Front and rear rails 52, 5
4 and base 56 are preferably integrally formed with one another, to which the top 62 may be suitably joined, for example by brazing, to form a closed flow duct 64. The base 56 has a plurality of circumferentially spaced discharge holes 66 that allow cooling fluid 68 to flow from the duct 64 to the shroud 42.
To help cool the shroud.
【００１６】一実施例において、冷却流体６８は、圧縮
機１４から放出されそして回収熱交換器３０内で加熱さ
れる前の圧縮空気流３４の一部分である。図１を再度参
照するに、従来の供給導管７０が圧縮機１４の出口と連
通するように適当に設けられて圧縮空気流３４の一部分
を受入れそして圧縮空気流３４を冷却流体６８としてシ
ュラウド支持体３８の近辺でケーシング２８を貫通する
ように放出する。再び図２を参照するに、供給導管７０
はケーシング２８を貫通した状態でそれに従来のように
接合されており、冷却流体６８を弧状マニホルド７２内
に送り込む。このマニホルドは下流方向に面するマニホ
ルド出口７４を有する。製造しかつ試験した一実施例で
は、冷却流体６８を単に、取付けフランジ４８と、高圧
ノズルをケーシング２８に保持する環状取付けフランジ
７６との間に通して参考ハンガに導きそれを冷却した。
参考ハンガはハンガ４６と実質的に同じであるが、頂部
６２を設けてないもので、図３に４６ｂで示してある。
冷却流体は参考ハンガ４６ｂにその全周に沿ってほぼ半
径方向内方に流入しそして参考ハンガ４６ｂを単純な対
流冷却により冷却した。In one embodiment, the cooling fluid 68 is a portion of the compressed air stream 34 prior to being discharged from the compressor 14 and heated in the recovery heat exchanger 30. Referring again to FIG. 1, a conventional feed conduit 70 is suitably provided to communicate with the outlet of compressor 14 to receive a portion of compressed air stream 34 and to use compressed air stream 34 as cooling fluid 68 for the shroud support. Discharge through the casing 28 in the vicinity of 38. Referring again to FIG. 2, the supply conduit 70
Is conventionally joined to the casing 28 through it and directs the cooling fluid 68 into the arcuate manifold 72. The manifold has a downstream facing manifold outlet 74. In one embodiment manufactured and tested, the cooling fluid 68 was simply passed between the mounting flange 48 and an annular mounting flange 76 which held the high pressure nozzle in the casing 28 and directed to a reference hanger to cool it.
The reference hanger is substantially the same as the hanger 46, but without the top 62, and is shown at 46b in FIG.
The cooling fluid entered the reference hanger 46b approximately radially inward along its entire circumference and cooled the reference hanger 46b by simple convection cooling.
【００１７】他の参考ハンガ実施例では、やはり図３に
示したＵ形衝突邪魔板７８が考えられ、この場合、冷却
空気６８は衝突邪魔板７８を通るように半径方向内方に
導かれてハンガ４６ｂの衝突冷却に用いられた。In another reference hanger embodiment, a U-shaped impingement baffle 78, also shown in FIG. 3, is contemplated, in which case cooling air 68 is directed radially inward through impingement baffle 78. It was used for collision cooling of the hanger 46b.
【００１８】図４は時間に対する半径方向膨張を例示す
るグラフで、第１時点Ｔ1 から第２時点Ｔ2 までの低出
力から高出力に至るバースト状態における過渡応答の一
例について翼端４４ｂで測定した半径方向膨張をロータ
曲線８０で示す。図３に示した参考ハンガ４６ｂに衝突
邪魔板７８を設けない場合にシュラウド４２の内面で測
定した対応半径方向膨張を図４に破線の参考シュラウド
曲線８２で示す。この半径方向膨張は、主として、シュ
ラウドを支持するハンガの熱変位によるものである。シ
ュラウド４２と翼端４４ｂとの間の最小半径方向間隙Ｃ
1 の狭点（pinch point)が狭点時点Ｔp に示されてい
る。狭点間隙Ｃ1 がエンジン１０のこの実施例で発生す
るのは、ロータの動翼４４がシュラウド４２より速く膨
張するからであり、動翼４４のロータ時定数τr はシュ
ラウド支持体３８のシュラウド支持体時定数τs より少
ない。換言すると、シュラウド支持体３８は動翼４４に
比べて熱応答が遅い。FIG. 4 is a graph illustrating the radial expansion with respect to time. An example of the transient response in a burst state from low power to high power from the first time point T 1 to the second time point T 2 was measured at the tip 44b. The radial expansion done is shown by the rotor curve 80. The corresponding radial expansion measured on the inner surface of the shroud 42 when the reference hanger 46b shown in FIG. 3 is not provided with the collision baffle 78 is shown in FIG. 4 by the dashed reference shroud curve 82. This radial expansion is primarily due to the thermal displacement of the hangers that support the shroud. Minimum radial clearance C between shroud 42 and tip 44b
A pinch point of 1 is shown at the narrow point time point T p . The narrow point clearance C 1 occurs in this embodiment of the engine 10 because the rotor blades 44 expand faster than the shroud 42, and the rotor time constant τ r of the rotor 44 is the shroud support 38 shroud. Less than the support time constant τ s . In other words, shroud support 38 has a slower thermal response than blade 44.
【００１９】熱時定数τは次式で表すことができる。The thermal time constant τ can be expressed by the following equation.
【００２０】τ＝ｍＣp ／（ｈＡ） ただし、ｍは冷却されているシュラウド支持体の質量
で、例えば、冷却中のハンガ４６の質量で表されうるも
のであり、Ｃp は冷却流体または空気６８の比熱であ
り、Ａは冷却流体６８を受ける面積、例えば、前側およ
び後ろ側レール５２、５４とベース５６の内面の面積で
あり、ｈは熱伝達率である。時定数τは、例えば、過渡
状態発生開始から翼端４４ｂとシュラウド４２の新しい
定常状態半径方向位置の約６２％に達するまでに要する
時間を表す。Τ = mC p / (hA) where m is the mass of the shroud support being cooled, which can be represented, for example, by the mass of the hanger 46 during cooling, and C p is the cooling fluid or air. Is the specific heat of 68, A is the area receiving the cooling fluid 68, for example, the area of the inner surfaces of the front and rear rails 52, 54 and the base 56, and h is the heat transfer coefficient. The time constant τ represents, for example, the time required from the start of the transient state to reach about 62% of the new steady state radial position of the blade tip 44b and shroud 42.
【００２１】本発明の一目的によれば、翼端４４ｂと、
ハンガ４６により支持されたシュラウド４２とにおける
熱膨張応答の整合の改良が望まれ、これはシュラウド支
持体３８の時定数τs を動翼４４の時定数τr に対して
減らすことにより達成されうる。邪魔板７８からの衝突
冷却の場合の熱伝達率ｈは従来約１０００BTU/(hr ・ft
2 ・゜F)程度であり、これが時定数に与える影響は、ｍと
Ｃp とＡによる小さな影響に比べてかなり大きい。従っ
て、時定数τs はｍとＡの値の実際の変化にはほとんど
影響されないが、熱伝達率ｈの変化には過度に敏感であ
る。そして、定常状態運転と過渡運転の両方に対する設
計は衝突冷却の場合いっそう困難である。According to one object of the present invention, a wing tip 44b,
An improved match of the thermal expansion response with the shroud 42 supported by the hangers 46 is desired, which can be achieved by reducing the time constant τ s of the shroud support 38 relative to the time constant τ r of the blade 44. . The heat transfer coefficient h in the case of collision cooling from the baffle plate 78 is about 1000 BTU / (hr.ft
2 ° F.), which has a much larger effect on the time constant than the small effects of m, C p and A. Therefore, the time constant τ s is hardly affected by the actual changes in the values of m and A, but is overly sensitive to changes in the heat transfer coefficient h. And designing for both steady state and transient operation is more difficult with impingement cooling.
【００２２】冷却流体６８を図３に示した参考ハンガ４
６ｂ内に半径方向に導入することによって得られる熱伝
達率ｈは、邪魔板７８がない場合、約４〜８BTU/(hr ・
ft2 ・゜F)であり、その結果、図４に示した参考シュラウ
ド曲線８２が得られた。しかし、シュラウド４２と動翼
４４との時定数の差により、過渡運転中依然として比較
的小さな翼端間隙狭点が生じる。また、前側および後ろ
側レール５２、５４の温度に比較的大きな周方向変化が
観察された。これは導入された回収熱交換器空気流３４
ｂの影響によるものである。The reference hanger 4 shown in FIG.
The heat transfer coefficient h obtained by introducing radially into 6b is about 4 to 8 BTU / (hr.
ft 2 · ° F), and as a result, the reference shroud curve 82 shown in FIG. 4 was obtained. However, due to the time constant difference between shroud 42 and blade 44, a relatively small tip clearance narrowing occurs during transient operation. In addition, a relatively large circumferential change was observed in the temperature of the front and rear rails 52, 54. This is due to the introduction of the recovered heat exchanger air stream 34
This is due to the influence of b.
【００２３】本発明の一目的によれば、図２に示したハ
ンガ４６は頂部６２を含むことが好ましく、これにより
密閉流れダクト６４が形成され冷却流体６８を従来周知
の管流として通しうる。頂部の開いた参考ハンガ４６ｂ
の衝突冷却および対流冷却されるものはいずれも望まし
くないとして使用されず、前者の場合の熱伝達率ｈより
小さくそして後者の場合のそれより大きい熱伝達率ｈを
用いることにより、ハンガ４６によるシュラウド４２の
時定数τs をより正確に制御してシュラウド４２と翼端
４４ｂとの間の熱応答をより良く整合しうる。In accordance with one object of the present invention, the hanger 46 shown in FIG. 2 preferably includes a top portion 62 which forms a closed flow duct 64 through which the cooling fluid 68 can pass as a well known tube flow. Reference hanger 46b with the top open
Both the impingement-cooled and convection-cooled, which are undesired, are not used and by using a heat transfer coefficient h that is less than the heat transfer coefficient h in the former case and greater than that in the latter case, the shroud by the hanger 46 is The time constant τ s of 42 may be more precisely controlled to better match the thermal response between shroud 42 and tip 44b.
【００２４】ハンガ４６を図２に示すように頂部６２で
密閉することにより、また、冷却流体６８をハンガ流れ
ダクト６４内で周方向に導いてハンガ４６を冷却する手
段８４を設けることにより、周知の管流が流れダクト６
４内に発生しそして本発明により有効に用いられてハン
ガ４６と動翼４４との時定数をより良く整合し、過渡応
答中翼端間隙狭点をより良く制御、例えば、増大する等
の利点をもたらす。2 by sealing the hanger 46 at the top 62 as shown in FIG. 2 and by providing means 84 for circumferentially guiding the cooling fluid 68 within the hanger flow duct 64 to cool the hanger 46. Pipe flow of the duct 6
4 and used effectively in accordance with the present invention to better match the time constants of the hanger 46 and the blade 44, and to better control, eg, increase, the tip clearance narrow point during transient response. Bring
【００２５】さらに詳述すると、本発明の一実施例によ
れば、冷却手段８４は図２と図５と図６に例示したよう
に、複数の周方向に相隔たる冷却流体出口８６、例え
ば、第１、第２、第３および第４流体出口８６ａ、８６
ｂ、８６ｃ、８６ｄを含み、これらの流体出口はハンガ
ダクト６４内に適切に配置され、全てが一方の周方向
（図６に示すように時計方向）だけに面して冷却流体６
８をダクト６４内で周方向に放出して単一方向の管流を
発生し、この管流に関するハンガ４６の時定数τs は動
翼４４の時定数τr とより良く整合するように減らされ
得る。製造されかつ試験されたハンガ４６の一実施例で
あって冷却手段８４を含むものでは、図４に示したよう
な改良シュラウド曲線８８が得られ、これはロータ曲線
８０とより良く整合し、そして同じ狭点時点Ｔp での翼
端間隙狭点Ｃ2 が拡大している。ハンガ４６による時定
数τs は、図４に示したシュラウド曲線８８とロータ曲
線８０との間のより均等な間隔によって示されるよう
に、動翼４４の時定数τr とより良く整合する。More specifically, in accordance with one embodiment of the present invention, the cooling means 84 includes a plurality of circumferentially spaced cooling fluid outlets 86, eg, as illustrated in FIGS. First, second, third and fourth fluid outlets 86a, 86
b, 86c, 86d, these fluid outlets are suitably arranged in the hanger duct 64, all facing only one circumferential direction (clockwise as shown in FIG. 6).
8 is discharged circumferentially in the duct 64 to produce a unidirectional tube flow, the time constant τ s of the hanger 46 for this tube flow is reduced to better match the time constant τ r of the blade 44. Can be done. One embodiment of the hanger 46 that has been manufactured and tested and that includes the cooling means 84 results in an improved shroud curve 88 as shown in FIG. 4, which better matches the rotor curve 80, and The blade tip clearance narrow point C 2 at the same narrow point time point T p is expanded. The time constant τ s by the hanger 46 better matches the time constant τ r of the blade 44, as shown by the more uniform spacing between the shroud curve 88 and the rotor curve 80 shown in FIG.
【００２６】図５と図６を再び参照するに、流体出口８
６は簡単なオリフィスでよく、好ましくは等間隔で相隔
たり、例えば、中心線１２から共通半径の所で等角度で
相隔たり、流れダクト６４内の冷却流体６８の周方向速
度を概して均等にする。一つ以上の流体出口８６を用い
得るが、少なくとも２つの流体出口８６が好適であり、
両出口は約１８０度隔てられて流体６８の速度分布をほ
ぼ均等にする。というのは、流体６８は出口８６の一つ
から流れダクト６４を経て他の出口８６まで流れるから
である。もちろん、もっと多くの出口８６を流れダクト
６４内に設ければ、流体６８の周方向速度はそれだけ均
等になる。なぜなら、それに応じて、一つの出口８６か
ら次の出口８６までの流体６８の質量流量が少なくなる
からである。Referring again to FIGS. 5 and 6, the fluid outlet 8
6 may be simple orifices, preferably equidistantly spaced, eg equiangularly spaced from the centerline 12 at a common radius, to generally equalize the circumferential velocity of the cooling fluid 68 in the flow duct 64. . Although more than one fluid outlet 86 may be used, at least two fluid outlets 86 are preferred,
The two outlets are separated by about 180 degrees to make the velocity distribution of the fluid 68 substantially uniform. The fluid 68 flows from one of the outlets 86 through the flow duct 64 to the other outlet 86. Of course, the more outlets 86 provided in the flow duct 64, the more evenly the circumferential velocity of the fluid 68 will be. This is because the mass flow rate of the fluid 68 from one outlet 86 to the next outlet 86 is correspondingly reduced.
【００２７】従来知られているように、時定数τは熱伝
達率ｈに反比例しそして熱伝達率ｈは冷却流体６８の速
度に正比例するので、出口８６の周方向配置は、ハンガ
４６近辺に導かれる回収熱交換器空気流３４ｂの周方向
に沿って変わる温度によるハンガ４６の環境温度の周方
向変化に応じてハンガ４６の様々な冷却度をもたらすよ
うに予め選定されうる。さらに、冷却流体６８を、図３
に示した参考ハンガ４６ｂの具体例で生じるように流れ
ダクト６４の全周に沿って半径方向に流れダクト６４内
に導入する代りに、流れダクト６４内で周方向に導くこ
とにより、比較的大きな熱伝達率ｈが得られる。As is known in the art, the time constant τ is inversely proportional to the heat transfer coefficient h, and the heat transfer coefficient h is directly proportional to the speed of the cooling fluid 68. Therefore, the circumferential arrangement of the outlet 86 is close to the hanger 46. It may be preselected to provide different degrees of cooling of the hanger 46 in response to circumferential changes in the ambient temperature of the hanger 46 due to the circumferentially varying temperature of the guided recovery heat exchanger airflow 34b. Further, cooling fluid 68 is added to FIG.
Instead of being introduced radially into the flow duct 64 along the entire circumference of the flow duct 64 as occurs in the embodiment of the reference hanger 46b shown in FIG. The heat transfer coefficient h is obtained.
【００２８】例えば、図２に示したハンガ４６の熱伝達
解析によれば、熱伝達率ｈは約４０BTU/(hr ・ ft2 ・゜F)
と推定され、これに比べ、図３に示した参考ハンガ４６
ｂに衝突邪魔板７８を用いない場合の熱伝達率ｈは約４
〜８BTU/(hr ・ ft2 ・゜F)程の小さな値となる。改善され
た熱伝達率ｈは、ハンガ４６による時定数τs をかなり
減らして動翼４４の時定数τr とより良く整合しそして
ハンガ４６の温度の周方向変化を減らすのに有効であ
り、従って、翼端間隙Ｃの周方向変化を効果的に減ら
す。For example, according to the heat transfer analysis of the hanger 46 shown in FIG. 2, the heat transfer coefficient h is about 40 BTU / (hr · ft 2 · ° F).
It is estimated that the reference hanger 46 shown in FIG.
When the collision baffle 78 is not used for b, the heat transfer coefficient h is about 4
The value is as small as ~ 8BTU / (hr · ft 2 · ° F). The improved heat transfer coefficient h is effective in significantly reducing the time constant τ s by the hanger 46 to better match the time constant τ r of the blade 44 and in reducing circumferential changes in the temperature of the hanger 46. Therefore, the change in the blade tip clearance C in the circumferential direction is effectively reduced.
【００２９】４つの流体出口８６の各々に冷却流体を送
給するために、冷却手段８４は、図２と図５と図６に示
したように、対応する複数のの出口管９０、例えば、第
１、第２、第３および第４出口管９０ａ、９０ｂ、９０
ｃ、９０ｄをさらに含む。これらの出口管９０はそれぞ
れの流体出口８６を含み、出口８６はハンガダクト６４
内のそれぞれの出口管のさもなくば閉ざされている末端
に設けられ、全出口が同じ周方向に面している。出口管
９０は、好ましくは、流れダクト６４内からほぼ軸方向
に後方に延在し、後ろ側レール５４を貫通し、次いでそ
れぞれ湾曲して取付けフランジ４８の筒形部４８ｂに沿
いかつ中心線１２の周りに同軸的に周方向に延びるよう
に形成される。To deliver cooling fluid to each of the four fluid outlets 86, the cooling means 84 includes a plurality of corresponding outlet tubes 90, eg, as shown in FIGS. 2, 5 and 6. First, second, third and fourth outlet tubes 90a, 90b, 90
c, 90d are further included. These outlet tubes 90 include respective fluid outlets 86, the outlets 86 being the hanger ducts 64.
Provided at the otherwise closed ends of the respective outlet pipes therein, all outlets face the same circumferential direction. Outlet tubes 90 preferably extend generally axially rearward from within flow duct 64, extend through rear rail 54, and then are each curved along tubular portion 48b of mounting flange 48 and along centerline 12. Is formed so as to extend coaxially around the circumference in the circumferential direction.
【００３０】冷却手段８４は複数の供給管９２、例え
ば、第１および第２供給管９２ａ、９２ｂをさらに含
み、各供給管はそれに対応する１対の出口管９０に冷却
流体６８を導くように作用する。図６と図７に示すよう
に、両供給管９２はそれぞれの入口９４ａ、９４ｂを有
し、両入口は隣合って配置され共通マニホルド７２の出
口７４と連通してそれから冷却流体６８を受入れる。両
供給管９２はそれぞれの出口９６ａ、９６ｂを有し、各
出口は対応する管９０の近接端にある１対の入口９８と
連通するように配置されている。すなわち、第１および
第２出口管入口９８ａ、９８ｂが第１供給管出口９６ａ
に接続され、そして第３および第４出口管入口９８ｃ、
９８ｄが第２供給管出口９６ｂに接続されている。各供
給管９２は、好ましくは、それに対応する出口管９０か
らほぼ半径方向外方に延在して取付けフランジ筒形部４
８ｂを貫通し、次いで中心線１２の周りにほぼ同軸的に
周方向にある円弧距離だけ延び、さらに隣の供給管９２
の対応部分近くで半径方向上方に曲がって供給管入口９
４ａ、９４ｂに至りそこでマニホルド７２と連通するよ
うに形成される。The cooling means 84 further includes a plurality of supply tubes 92, eg, first and second supply tubes 92a, 92b, each supply tube directing the cooling fluid 68 to a corresponding pair of outlet tubes 90. To work. As shown in FIGS. 6 and 7, both supply pipes 92 have respective inlets 94a, 94b, which are arranged next to each other and communicate with the outlet 74 of the common manifold 72 to receive the cooling fluid 68 therefrom. Both supply pipes 92 have respective outlets 96a, 96b, each outlet arranged to communicate with a pair of inlets 98 at the proximal ends of the corresponding pipes 90. That is, the first and second outlet pipe inlets 98a and 98b are the first supply pipe outlet 96a.
And third and fourth outlet pipe inlets 98c,
98d is connected to the second supply pipe outlet 96b. Each supply tube 92 preferably extends generally radially outwardly from its corresponding outlet tube 90 to provide a mounting flange tubular section 4.
8b, and then extends approximately coaxially about the centerline 12 for an arc distance in the circumferential direction, and further adjoins the supply pipe 92.
Bent upwards in the radial direction near the corresponding part of the supply pipe inlet 9
4a, 94b, where they are formed so as to communicate with the manifold 72.
【００３１】出口管９０と供給管９２の上述の形状は、
冷却流体６８を共通マニホルド７２から４つの周方向に
相隔たる流体出口８６に導くのに好適である。管９０、
９２は、第１に、冷却流体６８を流れダクト６４に導く
いっそう直接的な通路として、回収熱交換器空気流３４
ｂによる冷却流体６８の間接加熱を減らすのに好適であ
る。こうして、比較的低温の圧縮空気流３４を冷却流体
６８として流れダクト６４に供給することができ、その
際、冷却流体の経路に沿う吸熱による温度上昇は比較的
わずかであり、また冷却流体６８のハンガ４６への流れ
からの漏れは発生しない。The above-described shapes of the outlet pipe 90 and the supply pipe 92 are as follows.
It is suitable to direct the cooling fluid 68 from the common manifold 72 to four circumferentially spaced fluid outlets 86. Tube 90,
92 firstly serves as a more direct passage for the cooling fluid 68 to the flow duct 64 and serves as a recovery heat exchanger air stream 34.
It is suitable for reducing indirect heating of the cooling fluid 68 by b. In this way, the relatively cool compressed air stream 34 can be supplied to the flow duct 64 as the cooling fluid 68, the temperature rise due to the heat absorption along the path of the cooling fluid being relatively small, and of the cooling fluid 68. No leakage from the flow to the hanger 46 occurs.
【００３２】さらに、冷却流体６８を４つの流体出口８
６の各々において所定温度で供給することも望ましく、
各出口の流体温度は本発明の一実施例によれば実質的に
均等である。従って、マニホルド７２における供給管入
口９４ａ、９４ｂからそれぞれの供給管９２と出口管９
０を経て４つの流体出口８６に達する４つの流路がそれ
ぞれ流路長、すなわち、第１、第２、第３、第４流路長
Ｌ1 、Ｌ2 、Ｌ3 、Ｌ4 を有しそしてこれらの流路長は
ほぼ相等しいことが好ましい。Further, the cooling fluid 68 is supplied to the four fluid outlets 8
It is also desirable to supply at a predetermined temperature in each of 6,
The fluid temperature at each outlet is substantially equal, according to one embodiment of the invention. Therefore, from the supply pipe inlets 94a and 94b in the manifold 72, the respective supply pipes 92 and outlet pipes 9 are provided.
Each of the four flow paths reaching the four fluid outlets 86 via 0 has a flow path length, that is, a first, a second, a third, and a fourth flow path length L 1 , L 2 , L 3 , L 4 . And it is preferable that these flow path lengths are substantially the same.
【００３３】図７は冷却流体６８を入口９４ａ、９４ｂ
からそれぞれの流体出口８６ａ、８６ｂ、８６ｃ、８６
ｄに導く供給管９２と出口管９０の概略を示す。４つの
流路長Ｌ1 、Ｌ2 、Ｌ3 、Ｌ4 も示してある。供給管９
２と出口管９０は、この実施例では、４つの出口８６か
ら出る冷却流体６８の温度をほぼ均等にするような所定
の寸法と形状を有する。出口管９０と供給管９２は、
（図２に示したように）流路５０内に配置されるので、
回収熱交換器空気流３４ｂにより加熱される。しかし、
管９０、９２はフランジ７６により保護されており回収
熱交換器空気流３４ｂに直接露出されない。また、実質
的に等しい流路長Ｌ1 〜Ｌ4 を設けることにより、管９
０、９２を通る冷却流体６８の吸熱量はほぼ等しいの
で、冷却流体６８は共通温度で出口８６から放出され
る。従って、ダクト６４を通る冷却流体６８によるハン
ガ４６の熱膨縮は比較的均等であり、周方向のひずみと
それに伴う翼端間隙Ｃの周方向変化を減らし得る。In FIG. 7, the cooling fluid 68 is introduced into the inlets 94a and 94b.
From the respective fluid outlets 86a, 86b, 86c, 86
The outline of the supply pipe 92 and the outlet pipe 90 leading to d is shown. Also shown are four flow path lengths L 1 , L 2 , L 3 , L 4 . Supply pipe 9
2 and the outlet tube 90 are of a predetermined size and shape in this embodiment to approximately equalize the temperature of the cooling fluid 68 exiting the four outlets 86. The outlet pipe 90 and the supply pipe 92 are
Since it is located in the channel 50 (as shown in FIG. 2),
It is heated by the recovery heat exchanger airflow 34b. But,
The tubes 90, 92 are protected by the flange 76 and are not directly exposed to the recovered heat exchanger airflow 34b. Further, by providing the substantially equal flow path lengths L 1 to L 4 , the pipe 9
The heat absorptions of the cooling fluid 68 passing through 0 and 92 are almost equal, so that the cooling fluid 68 is discharged from the outlet 86 at a common temperature. Therefore, the thermal expansion and contraction of the hanger 46 by the cooling fluid 68 passing through the duct 64 is relatively uniform, and it is possible to reduce the circumferential strain and the accompanying circumferential change in the blade tip clearance C.
【００３４】図７に概略的に示すように、この実施例に
おいて等しい流路長Ｌ1 〜Ｌ4 を得るために、４つの流
体出口８６は約９０度ずつ周方向に相隔たっており、ま
た供給管出口９６ａ、９６ｂは好ましくは約１８０度相
隔たっておりそして流体出口８６のうちの対応出口間に
約４５度の間隔で配置されている。さらに、第１および
第２供給管入口９４ａ、９４ｂは第１および第２供給管
出口９６ａ、９６ｂそれぞれから周方向に約９０度隔た
っている。また第１および第２出口管９０ａ、９０ｂ
は、好ましくは、第３および第４出口管９０ｃ、９０ｄ
と対向するようにそれらから周方向に隔てられる。そう
すると、第１および第２供給管９２ａ、９２ｂと、それ
ぞれに接続された出口管は互いに重なり合わない。As shown schematically in FIG. 7, in order to obtain equal flow path lengths L 1 -L 4 in this embodiment, the four fluid outlets 86 are circumferentially spaced by about 90 degrees and are also fed. The tube outlets 96a, 96b are preferably about 180 degrees apart and are spaced about 45 degrees apart between corresponding ones of the fluid outlets 86. Further, the first and second supply pipe inlets 94a, 94b are circumferentially separated from the first and second supply pipe outlets 96a, 96b by about 90 degrees. Also, the first and second outlet pipes 90a, 90b
Are preferably third and fourth outlet tubes 90c, 90d.
Circumferentially separated from them so as to face. Then, the first and second supply pipes 92a and 92b and the outlet pipes connected to each other do not overlap each other.
【００３５】さらに、出口管９０と供給管９２の諸部を
中心線１２の周りに周方向に配置することにより管の熱
膨縮に対処し、管に誘起される熱応力を減らし得る。熱
膨縮による出口管９０の熱応力をさらに減らすために、
各出口管９０は好ましくはほぼＵ形の段部１００を含
み、この段部は取付けフランジ筒形部４８ｂ近辺の出口
管の周方向延在部分において軸方向に張り出している。
段部１００は図６と図８に示され、図８はシュラウド支
持体３８から除去した出口管９０と供給管９２の斜視図
である。Further, by arranging parts of the outlet pipe 90 and the supply pipe 92 in the circumferential direction around the center line 12, it is possible to cope with thermal expansion and contraction of the pipe and reduce thermal stress induced in the pipe. In order to further reduce the thermal stress of the outlet pipe 90 due to thermal expansion and contraction,
Each outlet tube 90 preferably includes a generally U-shaped step 100 that extends axially in the circumferentially extending portion of the outlet tube near the mounting flange tubular portion 48b.
Step 100 is shown in FIGS. 6 and 8, which is a perspective view of outlet tube 90 and supply tube 92 removed from shroud support 38.
【００３６】従って、上述の改良されたタービンシュラ
ウド支持体３８は、動翼４４の半径方向移動に関する時
定数をハンガ４６によるシュラウド４２の半径方向移動
に関する時定数とより良く整合するように作用しそして
過渡運転中翼端間隙狭点を効率的に拡大する。さらに、
ハンガ４６の温度の周方向変化も減らされてハンガ４６
の真円度が高まり、そして翼端間隙Ｃの対応周方向変化
が減少する。また、本発明によるシュラウド支持体３８
による改良された冷却効果は、前側および後ろ側レール
５２、５４間の温度差の低減に有効であり、これも、前
側と後ろ側のレール５２、５４間の半径方向移動差によ
る翼端間隙Ｃの対応変化を減らす。Accordingly, the improved turbine shroud support 38 described above acts to better match the time constant for radial movement of the blade 44 with the time constant for radial movement of the shroud 42 by the hanger 46, and Efficiently expand the tip clearance narrow point during transient operation. further,
Circumferential changes in the temperature of the hanger 46 are also reduced, and the hanger 46
Roundness increases, and the corresponding circumferential change in blade tip clearance C decreases. Also, the shroud support 38 according to the present invention.
The improved cooling effect due to is effective in reducing the temperature difference between the front and rear rails 52 and 54, which is also due to the difference in the radial tip between the front and rear rails 52 and 54 in the blade tip clearance C. Correspondence of change is reduced.
【００３７】以上、本発明の好適実施例と考えられるも
のを説明したが、もちろん、様々な改変が本発明の範囲
内で可能である。While what has been considered to be the preferred embodiments of the invention has been described above, of course, various modifications are possible within the scope of the invention.
【図１】本発明の一実施例によるタービンシュラウド支
持体を含む回収熱交換器付きガスタービンエンジンの一
例の概略縦断面図である。FIG. 1 is a schematic vertical cross-sectional view of an example of a gas turbine engine with a recovery heat exchanger including a turbine shroud support according to an embodiment of the present invention.
【図２】本発明の一実施例による図１に示したエンジン
用のタービンシュラウド支持体の拡大縦断面図である。2 is an enlarged vertical cross-sectional view of a turbine shroud support for the engine shown in FIG. 1 according to one embodiment of the present invention.
【図３】参考例としてのシュラウド支持体の密閉されて
いないハンガと比較して、図２に示したシュラウド支持
体ハンガの一部を仮想線で示す斜視図である。FIG. 3 is a perspective view showing a part of the shroud support hanger shown in FIG. 2 in phantom lines, as compared to an unsealed hanger of the shroud support as a reference example.
【図４】ロータに対する図２に示したシュラウド支持体
と参考シュラウド支持体の時間に対する半径方向膨張を
示すグラフである。4 is a graph showing radial expansion of the shroud support shown in FIG. 2 and a reference shroud support shown in FIG. 2 for a rotor.
【図５】図２に示したシュラウド支持体の線５ー５に沿
う上流向き横断面図である。FIG. 5 is an upstream cross-sectional view of the shroud support shown in FIG. 2 taken along line 5-5.
【図６】図２に示したシュラウド支持体を部分的に仮想
線で示す後ろ向き斜視図である。FIG. 6 is a rear perspective view of the shroud support shown in FIG. 2 partially shown in phantom.
【図７】図２に示したシュラウド支持体の横断面図で、
出口管と供給管の相対位置の概略を示す。7 is a cross-sectional view of the shroud support shown in FIG.
The outline of the relative position of an outlet pipe and a supply pipe is shown.
【図８】図７に示した出口管と供給管の概略斜視図であ
る。8 is a schematic perspective view of an outlet pipe and a supply pipe shown in FIG.
２８ ケーシング ３８ シュラウド支持体 ４２ タービンシュラウド ４４ タービン動翼 ４６ ハンガ ５２、５４ レール ５６ ベース ６２ 環状頂部 ６４ ダクト ６６ 放出孔 ７２ マニホルド ８６、８６ａ、８６ｂ、８６ｃ、８６ｄ 冷却流体出口 ９０、９０ａ、９０ｂ、９０ｃ、９０ｄ 出口管 ９２、９２ａ、９２ｂ 供給管 ９８、９８ａ、９８ｂ、９８ｃ、９８ｄ 出口管入口 １００ Ｕ形段部 28 Casing 38 Shroud support 42 Turbine shroud 44 Turbine blade 46 Hanger 52, 54 Rail 56 Base 62 Annular top 64 Duct 66 Discharge hole 72 Manifold 86, 86a, 86b, 86c, 86d Cooling fluid outlet 90, 90a, 90b, 90c , 90d outlet pipe 92, 92a, 92b supply pipe 98, 98a, 98b, 98c, 98d outlet pipe inlet 100 U-shaped step
Claims (13)
であって、 環状ケーシングと、 このケーシングに固定されそれから半径方向内方に離隔
してそれとの間に環状流路を画成するもので、前記中心
線の周りに同軸的に配置され、そして複数の周方向に相
隔たるタービン動翼の半径方向上側に配置し得るシュラ
ウドを半径方向に支持するベースと、前記ベ―スから前
記環状流路に向って半径方向外側に延在し、かつ周方向
に延在する流れダクトとを有する、環状ハンガと、 一方の周方向への流れを得るために 冷却流体を前記ハン
ガダクト内で周方向に導くことにより前記ハンガを冷却
する手段とからなるシュラウド支持体。1. A shroud support having a longitudinal centerline, comprising: an annular casing fixed to the casing and spaced radially inwardly therefrom to define an annular flow path therebetween. Coaxially arranged around the center line and arranged in a plurality of circumferential directions
Shuras that can be placed radially above the separating turbine blades
The base that supports the wood in the radial direction and the front of the base.
Circumferentially, extending radially outward toward the annular flow path
A shroud support comprising an annular hanger having a flow duct extending into the hanger, and means for cooling the hanger by circumferentially guiding a cooling fluid in the hanger duct to obtain one circumferential flow. .
ト内に配置されそして一方の周方向に面して前記冷却流
体を前記ダクト内で周方向に放出する複数の周方向に相
隔たる冷却流体出口を含む、請求項１記載のシュラウド
支持体。2. The hanger cooling means includes a plurality of circumferentially spaced cooling fluid outlets disposed in the hanger duct and facing one circumferential direction for discharging the cooling fluid circumferentially in the duct. The shroud support of claim 1, comprising:
請求項２記載のシュラウド支持体。3. The shroud support of claim 2, wherein the fluid outlets are equidistantly spaced.
らに含み、これらの出口管はそれぞれ前記ハンガダクト
内のそれぞれの末端に設けた前記流体出口を有し、前記
出口管は前記複数の流体出口から放出し得る前記冷却流
体の温度を実質的に均等にするような所定の寸法と形状
を有する、請求項２記載のシュラウド支持体。4. The hanger cooling means further includes a plurality of outlet pipes, each of the outlet pipes having the fluid outlet provided at a respective end of the hanger duct, the outlet pipe having the plurality of fluid outlets. The shroud support of claim 2, having a predetermined size and shape to substantially equalize the temperature of the cooling fluid that can be discharged from the shroud support.
らに含み、各供給管は前記冷却流体を前記出口管の対応
する１対に導き、前記供給管は前記複数の流体出口から
放出し得る前記冷却流体の温度を実質的に均等にするよ
うに前記出口管とともに所定の寸法と形状を有する、請
求項４記載のシュラウド支持体。5. The hanger cooling means further comprises a plurality of supply pipes, each supply pipe directing the cooling fluid to a corresponding pair of outlet pipes, the supply pipes being capable of discharging from the plurality of fluid outlets. The shroud support of claim 4, having a predetermined size and shape with the outlet tube to substantially equalize the temperature of the cooling fluid.
れの出口管と、２本の前記供給管とを備え、各供給管は
前記冷却流体を受入れる入口を有し、前記２本の供給管
入口からそれぞれの供給管と出口管を経て前記４つの流
体出口に達する４つの流路の各々が流路長を有し、これ
らの４つの流路長はほぼ相等しい、請求項５記載のシュ
ラウド支持体。6. Four fluid outlets and four respective outlet tubes and two said supply tubes, each supply tube having an inlet for receiving said cooling fluid, said two supply tubes. The shroud of claim 5, wherein each of the four flow passages from the inlet to the four fluid outlets through respective feed and outlet pipes has a flow passage length, the four passage lengths being substantially equal. Support.
ており、 前記出口管の第１および第２管が前記中心線の周りにほ
ぼ同軸的に延在し、そして前記供給管の第１管の出口に
接続した入口を有し、 前記出口管の第３および第４管が前記中心線の周りにほ
ぼ同軸的に延在し、そして前記供給管の第２管の出口に
接続した入口を有し、また 前記第１および第２出口管は前記第３および第４出口管
と対向するようにそれらから周方向に隔たっている、請
求項６記載のシュラウド支持体。7. The four fluid outlets are equally spaced apart, the first and second tubes of the outlet tube extending substantially coaxially about the centerline, and the first of the supply tubes. An inlet having an inlet connected to an outlet of a tube, the third and fourth tubes of the outlet tube extending substantially coaxially about the centerline and connected to an outlet of a second tube of the supply tube 7. The shroud support according to claim 6, further comprising: and first and second outlet tubes circumferentially spaced from and opposite the third and fourth outlet tubes.
の周りにほぼ同軸的に延在し、そして両供給管の前記入
口は共通マニホルドから前記冷却流体を受入れるように
隣合っている、請求項７記載のシュラウド支持体。8. The first and second supply pipes extend substantially coaxially about the centerline, and the inlets of both supply pipes are adjacent to receive the cooling fluid from a common manifold. The shroud support according to claim 7.
向に相隔たっており、 前記第１および第２供給管出口
は約１８０度相隔たっておりそして前記流体出口のうち
の対応出口間に約４５度の間隔で配置されており、また
前記第１および第２供給管入口は前記第１および第２供
給管出口それぞれから約９０度隔たっている、請求項８
記載のシュラウド支持体。9. The four fluid outlets are circumferentially spaced by about 90 degrees, the first and second supply pipe outlets are spaced about 180 degrees, and between the corresponding ones of the fluid outlets. 9. 45 degrees apart, and said first and second feed tube inlets are spaced about 90 degrees from each of said first and second feed tube outlets.
The shroud support described.
あり、そして軸方向に相隔たりかつ前記ベースから半径
方向外方に延在する前側および後ろ側レールと、前記ベ
ースとほぼ平行に配置されてそれとの間に前記流れダク
トを画成する軸方向延在頂部とを含む、請求項９記載の
シュラウド支持体。10. The hanger is generally rectangular in cross-section and is positioned substantially parallel to the base with front and rear rails axially spaced apart and extending radially outward from the base. 10. The shroud support of claim 9 including an axially extending apex therebetween defining the flow duct.
クトから前記シュラウドに衝突させるように導く複数の
周方向に相隔たる放出孔を有する、請求項１０記載のシ
ュラウド支持体。11. The shroud support of claim 10, wherein the base has a plurality of circumferentially spaced discharge holes that guide the fluid from the flow duct to impinge on the shroud.
る段部を有する、請求項９記載のシュラウド支持体。12. The shroud support according to claim 9, wherein each outlet pipe has a step portion that allows thermal displacement of the outlet pipe.
あり、そして軸方向に相隔たりかつ前記ベースから半径
方向外方に延在する前側および後ろ側レールと、前記ベ
ースとほぼ平行に配置されてそれとの間に前記流れダク
トを画成する軸方向延在頂部とを含む、請求項２記載の
シュラウド支持体。13. The hanger is generally rectangular in cross-section and is positioned substantially parallel to the base with front and rear rails axially spaced apart and extending radially outward from the base. The shroud support of claim 2 including an axially extending apex therebetween defining the flow duct.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US666,959 | 1991-03-11 | ||
| US07/666,959 US5167487A (en) | 1991-03-11 | 1991-03-11 | Cooled shroud support |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH04303104A JPH04303104A (en) | 1992-10-27 |
| JPH0751888B2 true JPH0751888B2 (en) | 1995-06-05 |
Family
ID=24676243
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP4019345A Expired - Fee Related JPH0751888B2 (en) | 1991-03-11 | 1992-01-09 | Cooling shroud support |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US5167487A (en) |
| EP (1) | EP0503752B1 (en) |
| JP (1) | JPH0751888B2 (en) |
| CA (1) | CA2061939C (en) |
| DE (1) | DE69210077T2 (en) |
| IL (1) | IL100515A0 (en) |
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| BE756582A (en) * | 1969-10-02 | 1971-03-01 | Gen Electric | CIRCULAR SCREEN AND SCREEN HOLDER WITH TEMPERATURE ADJUSTMENT FOR TURBOMACHINE |
| US3807891A (en) * | 1972-09-15 | 1974-04-30 | United Aircraft Corp | Thermal response turbine shroud |
| US4127357A (en) * | 1977-06-24 | 1978-11-28 | General Electric Company | Variable shroud for a turbomachine |
| US4303371A (en) * | 1978-06-05 | 1981-12-01 | General Electric Company | Shroud support with impingement baffle |
| GB2047354B (en) * | 1979-04-26 | 1983-03-30 | Rolls Royce | Gas turbine engines |
| US4573865A (en) * | 1981-08-31 | 1986-03-04 | General Electric Company | Multiple-impingement cooled structure |
| GB2117451B (en) * | 1982-03-05 | 1985-11-06 | Rolls Royce | Gas turbine shroud |
| GB2125111B (en) * | 1982-03-23 | 1985-06-05 | Rolls Royce | Shroud assembly for a gas turbine engine |
| US4573866A (en) * | 1983-05-02 | 1986-03-04 | United Technologies Corporation | Sealed shroud for rotating body |
| US4553901A (en) * | 1983-12-21 | 1985-11-19 | United Technologies Corporation | Stator structure for a gas turbine engine |
| FR2576637B1 (en) * | 1985-01-30 | 1988-11-18 | Snecma | GAS TURBINE RING. |
| FR2597921A1 (en) * | 1986-04-24 | 1987-10-30 | Snecma | SECTORIZED TURBINE RING |
| GB2206651B (en) * | 1987-07-01 | 1991-05-08 | Rolls Royce Plc | Turbine blade shroud structure |
-
1991
- 1991-03-11 US US07/666,959 patent/US5167487A/en not_active Expired - Lifetime
- 1991-12-26 IL IL100515A patent/IL100515A0/en unknown
-
1992
- 1992-01-08 DE DE69210077T patent/DE69210077T2/en not_active Expired - Fee Related
- 1992-01-08 EP EP92300154A patent/EP0503752B1/en not_active Expired - Lifetime
- 1992-01-09 JP JP4019345A patent/JPH0751888B2/en not_active Expired - Fee Related
- 1992-02-27 CA CA002061939A patent/CA2061939C/en not_active Expired - Fee Related
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2047357A (en) * | 1979-04-27 | 1980-11-26 | Luk Lamellen & Kupplungsbau | Apparatus for selectively disconnecting and connecting a rotatable shaft |
Also Published As
| Publication number | Publication date |
|---|---|
| JPH04303104A (en) | 1992-10-27 |
| DE69210077D1 (en) | 1996-05-30 |
| EP0503752B1 (en) | 1996-04-24 |
| CA2061939A1 (en) | 1992-09-12 |
| DE69210077T2 (en) | 1996-12-19 |
| US5167487A (en) | 1992-12-01 |
| IL100515A0 (en) | 1992-09-06 |
| EP0503752A1 (en) | 1992-09-16 |
| CA2061939C (en) | 2002-05-28 |
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